Over-frame blanket assemblies and methods of installation in fuselage assemblies

ABSTRACT

Fuselage assemblies, over-frame blanket assemblies, and methods of installing over-frame blanket assemblies are provided. A fuselage assembly for an aircraft includes a fuselage skin, a cabin liner, and an over-frame blanket assembly. The cabin liner has an outer side facing the fuselage skin. The over-frame blanket assembly is disposed between the fuselage skin and the cabin liner and has a first blanket piece. The first blanket piece includes a first sound barrier layer that defines a first outer surface of the over-frame blanket assembly and a first sound absorbing layer that defines a second outer surface of the over-frame blanket assembly facing the fuselage skin. A method of installing the over-frame blanket assembly includes positioning the first blanket piece in an orientation such that the first sound barrier layer is directly adjacent the cabin liner.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application claims the benefit of U.S. Provisional Application No.61/970,224, filed Mar. 25, 2014. The disclosure of the above applicationis incorporated herein by reference.

TECHNICAL FIELD

The technical field relates generally to fuselage assemblies foraircraft and more particularly relates to fuselage assemblies withover-frame blanket assemblies and methods of installing over-frameblankets.

BACKGROUND

A conventional passenger aircraft includes a fuselage, a cabin interiorattached to and/or supported by the fuselage, and thermal/acousticinsulation bags or pieces in the fuselage frame bays between thefuselage frames. For further cabin noise reduction, an additionalsound-deadening blanket can be added between the fuselage structure andthe cabin liner. As the aircraft is flown, the fuselage interacts withthe atmosphere. This interaction generates vibration which, if leftunchecked, will be perceived by occupants of the aircraft as noise,which is undesirable. The sound-deadening blanket is used to suppressthe transmission of noise into the cabin. The sound-deadening blanket ispositioned to intercept the noise vibrations and is configured tosuppress the vibrations transmitted from the fuselage towards the cabin.

Conventional sound-deadening blankets have three layers through thedepth of the blanket. The three layers include a center layer of a soundbarrier material surrounded by two layers of sound absorbing material.The sound absorbing layers absorb sound compression waves that bouncebetween the sound barrier layer and the fuselage and between the soundbarrier layer and the cabin interior.

During the lifespan of the aircraft, it is often desirable to accesselectronic components, electrical wires, oxygen lines, or the like thatare located between the fuselage and the sound-deadening blanket. Suchaccess is often accomplished by cutting through the sound-deadeningblanket. Such cuts are typically taped back together with a tape appliedto the inner layer of the sound-deadening blanket. Taping the innerlayer typically results in increased sound transmission as contrastedwith the uncut sound-deadening blanket. Although these sound-deadeningblankets are adequate for their intended purpose, the need for improvedsound deadening in the cabin of the aircraft is essentially constant.

As such, it is desirable to provide sound deadening assemblies andmethods that provide improved ease of assembly and ease of repair. Inaddition, other desirable features and characteristics will becomeapparent from the subsequent summary and detailed description, and theappended claims, taken in conjunction with the accompanying drawings andthis background.

SUMMARY OF EMBODIMENTS

Various non-limiting embodiments of fuselage assemblies, over-frameblanket assemblies, and methods for installing over-frame blankets aredisclosed herein.

In a first non-limiting embodiment, a fuselage assembly for an aircraftincludes, but is not limited to, a fuselage skin, a cabin liner, and anover-frame blanket assembly. The cabin liner has an outer side facingthe fuselage skin. The over-frame blanket assembly is disposed betweenthe fuselage skin and the cabin liner and has a first blanket piece. Thefirst blanket piece includes a first sound barrier layer that defines afirst outer surface of the over-frame blanket assembly and a first soundabsorbing layer that defines a second outer surface of the over-frameblanket assembly facing the fuselage skin.

In a second non-limiting embodiment, an over-frame blanket assemblyincludes, but is not limited to, a first sound barrier layer and a firstsound absorbing layer. The first sound barrier layer defines a firstouter surface of the over-frame blanket assembly and the first soundabsorbing layer defines a second outer surface of the over-frame blanketassembly for facing a fuselage skin when installed in the fuselageassembly.

In a third non-limiting embodiment, a method for installing anover-frame blanket in a fuselage assembly of an aircraft includes, butis not limited to, providing a first blanket piece of the over-frameblanket assembly. The method further includes positioning the firstblanket piece in an orientation such that a first sound barrier layer isdirectly adjacent to a cabin liner. The method further still includessecuring the first blanket piece to the fuselage assembly in theorientation.

BRIEF DESCRIPTION OF THE DRAWINGS

Advantages of the present invention will be readily appreciated, as thesame becomes better understood by reference to the following detaileddescription when considered in connection with the accompanying drawingswherein:

FIG. 1 is a cross sectional view illustrating a non-limiting embodimentof a fuselage assembly in accordance with the teaching of the presentdisclosure;

FIG. 2A is a cross-sectional view illustrating an over-frame blanketjoint of the over-frame blanket assembly of FIG. 1;

FIG. 2B. is a front view illustrating the over-frame blanket joint ofFIG. 2A;

FIG. 3 is a front view illustrating an over-frame blanket joint of theover-frame blanket assembly of FIG. 1;

FIG. 4 is a cross-sectional view illustrating a retaining assembly ofthe over-frame blanket of FIG. 1;

FIG. 5 is a cross-sectional view illustrating a releasable soundabsorber secured to the over-frame blanket assembly of FIG. 1.

FIG. 6 is a front view of a non-limiting embodiment of a repairedportion of the over-frame blanket assembly of FIG. 1 in accordance withthe teachings of the present disclosure;

FIG. 7 is a block diagram illustrating a non-limiting embodiment of amethod for installing an over-frame blanket in a fuselage assembly inaccordance with the teachings of the present disclosure; and

FIG. 8 is a block diagram illustrating a non-limiting embodiment of amethod for repairing an over-frame blanket assembly is illustratedaccording to the teachings of the present disclosure.

DETAILED DESCRIPTION

The following detailed description is merely exemplary in nature and isnot intended to limit the invention or the application and uses of theinvention. Furthermore, there is no intention to be bound by any theorypresented in the preceding background or the following detaileddescription.

Various non-limiting embodiments of an improved over-frame blanketassembly, a fuselage assembly, and a method for installing an over-frameblanket assembly are disclosed herein. The over-frame blanket assemblyhas a first outer surface that is defined by a sound barrier layer.Seams, tears, apertures, and mounting assembly locations are morereadily apparent from visual inspection than in over-frame blanketassemblies that include a sound absorbing layer on an inner side of theover-frame blanket. Repairs and joints between blanket pieces are alsomore effectively sealed when the sound barrier layer defines the firstouter surface as contrasted with over-frame blankets with soundabsorbing layers on the inner side of the over-frame blanket.

A greater understanding of the fuselage assembly, over-frame blanketassembly, and method of installing the over-frame blanket assembly maybe obtained through a review of the illustrations accompanying thisapplication together with a review of the detailed description thatfollows.

FIG. 1 is a cross sectional view illustrating an embodiment of afuselage assembly 100 for an aircraft in accordance with the teachingsof the present disclosure. Fuselage assembly 100 includes a fuselageskin 110, a fuselage frame 120, thermal/acoustic insulation pieces 122,an over-frame blanket assembly 124, a retaining assembly 126, a cabinliner 128. Fuselage skin 110 forms the periphery of the aircraft andencloses an interior cabin cavity 112. During flight, a turbulentboundary layer (“TBL”) of air acts on fuselage skin 110 to createcompression waves on the inside of fuselage assembly 100. If leftunimpeded, TBL compression waves are transmitted to an interior cabin ofthe aircraft, resulting in a noisy cabin.

Fuselage frame 120 forms an inner support structure that supports aninner periphery of fuselage skin 110. Fuselage frame 120 includes framecaps 130 that project radially inwards away from fuselage skin 110.Fuselage frame 120 further defines frame bay cavities 123, in whichelectronics, communication cables, oxygen hoses, or other aircraftsystems may be located. In some embodiments, separate cable raceways(not shown) extend through frame bay cavities 123.

Thermal/acoustic insulation pieces 122 provide sound absorption of theTBL compression waves and thermal insulation of fuselage assembly 100.Thermal/acoustic insulation pieces 122 are disposed in cavities formedby fuselage frame 120. In the example provided, thermal/acousticinsulation pieces 122 are bags filled with fiberglass insulation. Itshould be appreciated that other materials may be utilized withoutdeparting from the scope of the present disclosure.

Referring now to FIGS. 2A and 2B, and with continued reference to FIG.1, an over-frame blanket joint 160 of over-frame blanket assembly 124 isillustrated in a cross sectional view and a front view in accordancewith the teachings of the present disclosure. Over-frame blanketassembly 124 includes a first outer surface 141, a second outer surface143, a first blanket piece 144, a second blanket piece 146, and anacoustic barrier patch 148.

First blanket piece 144 and second blanket piece 146 each include asound barrier layer 161 and a sound absorbing layer 162. In the exampleprovided, sound barrier layer 161 and sound absorbing layer 162 definean entire depth of over-frame blanket assembly 124 at each point ofover-frame blanket assembly 124 that is not part of a joint. Noadditional layers of sound absorbing material are included in theexample provided. In some embodiments, additional layers may be utilizedbetween sound barrier layer 161 and fuselage skin 110. In areas whereblanket pieces are joined with structural components or other blanketpieces, an entire depth of over-frame blanket assembly may be defined bythe respective blanket piece and acoustic barrier patch 148, as will beapparent from the description below.

Although only two blanket pieces are illustrated, it should beappreciated that as many blanket pieces as needed may be utilized toprovide substantially continuous sound damping throughout fuselageassembly 100. Sound barrier layer 161 is a dense layer with enough massto reflect a substantial portion of the TBL compression waves, as willbe appreciated by those with skill in the art. In the example provided,sound barrier layer 161 is a vinyl material. It should be appreciatedthat other materials may be utilized without departing from the scope ofthe present disclosure.

Sound barrier layer 161 defines a portion of first outer surface 141 ofover-frame blanket assembly 124 so that sound barrier layer 161 isexposed radially inward of over-frame blanket assembly 124 in theinstalled state illustrated in FIG. 1. For example, no further soundabsorbing layer 162 is included in over-frame blanket assembly 124radially inward of sound barrier layer 161. Accordingly, tears, splits,incisions, and other apertures in over-frame blanket assembly 124 arereadily apparent by visual inspection.

Sound absorbing layer 162 is less dense than sound barrier layer 161 toprovide sound absorption. Sound absorbing layer 162 defines second outersurface 143 of over-frame blanket assembly 124 facing fuselage skin 110.In the example provided, sound absorbing layer 162 is a felt materialpartially molded into sound barrier layer 161. It should be appreciatedthat other materials may be utilized and sound absorbing layer 162 maybe secured to sound barrier layer 161 in different configurations, suchas by adhesion, without departing from the scope of the presentdisclosure. In some embodiments, a hook fastener is secured to soundbarrier 161 so that the hooks directly fasten to releasable soundabsorber 190.

Acoustic barrier patch 148 is an acoustic barrier with propertiessimilar to sound barrier layer 161. In the example provided, acousticbarrier patch 148 is a single layer of vinyl material. It should beappreciated that additional layers disposed between sound barrier layer161 and sound absorbing layer 162, as well as different materials may beutilized without departing from the scope of the present disclosure.

Acoustic barrier patch 148 includes an adhesive layer 164 directlyadhered to the acoustic barrier material. In the example provided,acoustic barrier patch 148 is a roll of acoustic barrier material withtwo discrete adhesive strips on lateral edge portions 166 that expose alateral center portion 168 of acoustic barrier patch 148. It should beappreciated that adhesive layer 164 may cover an entire surface ofacoustic barrier patch 148 or may be applied separately withoutdeparting from the scope of the present disclosure. In some embodiments,adhesive layer 164 may be adhered to acoustic barrier patch 148 andcovered with a release liner until installation of acoustic barrierpatch 148 onto first blanket piece 144 and second blanket piece 146.

Referring again to FIG. 1, cabin liner 128 is disposed radially inwardof over-frame blanket assembly 124. Cabin liner 128 includes a cabininterior shell 154 and an acoustic absorber layer 156. Cabin interiorshell 154 faces the interior cabin cavity 112 of the aircraft andacoustic absorber layer 156 opposes first outer surface 141 ofover-frame blanket assembly 124. Cabin interior shell 154 is a layerthat forms part of the decorative portions, storage portions, or otherportions of the finished cabin of the aircraft. Acoustic absorber layer156 may be felt, foam, or other acoustic absorbing materials. In theexample provided, cabin liner 128 and over-frame blanket assembly 124are separated to form a liner cavity 158 in which compression waves mayreflect and be damped by acoustic absorber layer 156.

Referring now to FIG. 3, and with continued reference to FIG. 1, a frontview of an embodiment of an over-frame blanket joint 170 is illustratedin accordance with the teachings of the present disclosure. Over-frameblanket joint 170 illustrates a joint between first blanket piece 144and an outer portion 174 of a structural component 172 that passesthrough a depth of fuselage assembly 100. Structural component 172 maybe any component to which over-frame blanket assembly 124 is to beattached, such as the window illustrated in FIG. 3 or a floor liner asillustrated in FIG. 1. Over-frame blanket joint 170 is similar to thejoint 160 formed by acoustic barrier patch 148, first blanket piece 144,and second blanket piece 146 as illustrated in FIGS. 2A and 2B, wherelike numbers refer to like components. Over-frame blanket joint 170,however, adheres to first blanket piece 144 and outer portion 174 ofstructural component 172, as is most easily seen in FIG. 3.

Referring now to FIG. 4, a cross sectional view of an embodiment of aretaining assembly 126 is illustrated in accordance with the teachingsof the present disclosure. Retaining assembly 126 is similar to themounting assembly disclosed in US Patent Publication 20130175395, whichis hereby incorporated by reference as to the structure disclosedtherein, but not as to any term definitions used therein. In someembodiments, retaining assembly 126 incorporates a hard mounted spikefixed to fuselage frame 120.

Retaining assembly 126 includes a mounting block 180, a retaining spike182, and a retaining cap 184. Mounting block 180 is secured to frame 120and receives retaining spike 182. Retaining spike 182 and retaining cap184 cooperate to secure over-frame blanket assembly 124 to fuselageframe 120. For example, retaining cap 184 may be restricted fromseparating from retaining spike 182 by a barbed projection 185.

Retaining cap 184 includes a rigid layer 186 and a vibration isolatinglayer 188. Rigid layer 186 resists deformation and cooperates withbarbed projection 185 to limit separation of retaining cap 184 fromretaining spike 182. Vibration isolating layer 188 is a dampingmaterial, such as felt or foam, which restricts vibration transmissionbetween retaining cap 184 and sound barrier layer 161 of first blanketpiece 144. Vibration isolating layer 188 directly abuts sound barrierlayer 161 in the assembled state of retaining assembly 126 illustratedin FIG. 4 and fuselage assembly 100 illustrated in FIG. 1.

Referring now to FIG. 5, and with continued reference to FIG. 1, across-sectional view illustrates a releasable sound absorber 190 securedto over-frame blanket assembly 124. Releasable sound absorber 190,however, is a single layer secured in a releasable manner to over-frameblanket assembly 124. In the example provided, releasable sound absorber190 is segmented and non-continuous to readily facilitate removal ofreleasable sound absorber 190 during repair of electronics and otherequipment outboard of over-frame blanket assembly 124.

Releasable sound absorber 190 is secured to first outer surface 141 ofsound barrier layer 161 by releasable fasteners 192. In the exampleprovided, releasable fasteners 192 are hook and loop fasteners with oneside (one of hook or loop) adhered to releasable sound absorber 190 andanother side (the other of hook or loop) adhered to first outer surface141. It should be appreciated that other releasable fasteners may beutilized without departing from the scope of the present invention. Asused herein, releasable fastener refers means that the fastener iscapable of fully separating sound absorber 190 from over-frame blanketassembly 124 without puncturing or otherwise damaging sound absorber 190or over-frame blanket assembly 124.

In the example provided, retaining assembly 126 passes through andsecures releasable sound absorber 190. It should be appreciated that theretaining cap need not have a vibration isolating layer when utilized toabut releasable sound absorber 190. In other embodiments, releasablesound absorber 190 is not secured by retaining assembly 126. In someembodiments, releasable sound absorber 190 is reduced in size to act asa moisture absorber for any condensation that may build up on firstouter surface 141.

Referring now to FIG. 6, a front view of an embodiment of a repairedportion 200 of first blanket piece 144 is illustrated in accordance withthe teachings of the present disclosure. An aperture 210 in firstblanket piece 144 extends longitudinally between a first end 212 and asecond end 214. Aperture 210 may be a result of, for example, repair andmaintenance of components—such as oxygen lines and electronics—disposedbetween over-frame blanket assembly 124 and fuselage skin 110. Aperture210 is repaired by adherence of at least one acoustic barrier patch 148directly to sound barrier layer 161 of first blanket piece 144.

In the example provided, first, second, and third acoustic barrierpatches 148A, 148B, and 148C are applied in three locations to improvecontinuity of sound barrier material across the repaired portion 200.Acoustic barrier patches 148A-C are similar to acoustic barrier patch148, but have been renumbered for clarity of describing orientations ofthe three separate patches. First acoustic barrier patch 148A is appliedacross the entire length of aperture 210 between first end 212 andsecond end 214. Second acoustic barrier patch 148B is appliedperpendicular to first acoustic barrier patch 148A overtop first end 212of aperture 210. Third acoustic barrier patch 148C is appliedperpendicular to first barrier acoustic patch 148A overtop second end214 of aperture 210. Accordingly, TBL compression waves travelingthrough aperture 210 are limited by an adhered acoustic barrier materialin any direction along first outer surface 141 of over-frame blanketassembly 124. In some embodiments, second and third acoustic barrierpatches 148B, 148C are omitted when adhesive layer 164 covers an entiresurface of first acoustic barrier patch 148A.

Referring now to FIG. 7, a flow diagram illustrates an embodiment of amethod 300 for installing an over-frame blanket assembly in a fuselageassembly in accordance with the teachings of the present disclosure. Forexample, operations of method 300 may be performed by machines ortechnicians to install the over-frame blanket assembly.

Operation 302 provides a first blanket piece of an over-frame blanketassembly for the fuselage assembly. For example, operation 302 mayprovide first blanket piece 144 of over-frame blanket assembly 124.Operation 304 positions the first blanket piece in an orientation wherea first outer surface of the over-frame blanket assembly that is definedby an acoustic barrier of the first blanket piece faces an inner cabinof the fuselage assembly. For example, first blanket piece 144 may bepositioned with first outer surface 141 facing towards interior cabincavity 112.

Operation 306 presses the first blanket piece onto a retaining spikethat is mounted to a frame of the fuselage assembly. For example,operation 306 may press first blanket piece 144 onto retaining spike182. Operation 308 presses a retaining cap onto the retaining spike sothat a vibration isolating layer of the retaining cap abuts the soundbarrier layer of the first blanket piece. For example, operation 308 maypress retaining cap 184 onto retaining spike 182 so that vibrationisolating layer 188 abuts first outer surface 141 of over-frame blanketassembly 124.

Operation 310 adheres a first acoustic barrier patch to a first edgeportion of the sound barrier layer of the first blanket piece and to anouter portion of a structural component of the fuselage assembly. Forexample, acoustic barrier patch 148 may be adhered to first blanketpiece 144 and to outer portion 174 of structural component 172 asillustrated in FIGS. 1 and 4.

Operation 311 provides a second blanket piece of the over-frame blanketassembly. Operation 312 adheres a second acoustic barrier patch to thesecond edge portion of the sound barrier layer of the first blanketpiece. For example, operation 312 may adhere acoustic barrier patch 148to first blanket piece 144 and second blanket piece 146 as illustratedin FIGS. 1-3. Operation 313 secures a releasable sound absorber toover-frame blanket assembly in a releasable manner. For example,operation 313 may secure releasable sound absorber 190 to over-frameblanket assembly 124 with releasable fasteners 192.

Operation 314 secures a cabin liner so that an acoustic absorber layerof the cabin liner opposes the acoustic barrier of the first blanketpiece. It should be appreciated that additional operations, feweroperations, or alternative operations of method 300 may be performed insome embodiments. Furthermore, the order of operations may be differentfrom the order in which the operations are described herein.

Referring now to FIG. 8, a flow diagram of an embodiment of a method 400of repairing an over-frame blanket assembly is illustrated according tothe teachings of the present disclosure. For example, method 400 may beperformed by machines or technicians to create repaired portion 200 asillustrated in FIG. 6.

Operation 401 separates a releasable sound absorber from an over-frameblanket assembly. For example, operation 401 may separate releasableabsorber 190 using releasable fasteners 192.

Operation 402 visually inspects an exposed sound barrier layer of anover-frame blanket to identify an aperture in the over-frame blanket.For example, operation 402 may visually inspect first outer surface 141of first blanket piece 144 to identify aperture 210. Operation 404 cutsan acoustic barrier patch to a length that is longer than a length ofthe aperture and wider than a width of the aperture. For example, firstacoustic barrier patch 148A may be cut to be longer and wider than alength and a width of aperture 210.

Operation 406 exposes an adhesive layer of the acoustic barrier patch.For example, operation 406 may remove a release liner from adhesivelayer 164 of acoustic barrier patch 148A. Operation 408 presses theadhesive layer onto the sound barrier layer so that the acoustic barrierpatch entirely covers the aperture. For example, first acoustic barrierpatch 148A may be pressed onto first outer surface 141 to cover aperture210.

Operation 410 adheres a second acoustic barrier patch to a longitudinalend of the first acoustic barrier patch. For example, second acousticbarrier patch 148B may be adhered perpendicular to first acousticbarrier patch 148A at a first end 212 of aperture 210. Operation 412secures the releasable sound absorber to the over-frame blanketassembly. For example, operation 412 may secure releasable soundabsorber 190 to over-frame blanket assembly 124 using releasablefasteners 192 to cover acoustic barrier patches 148A-B.

While at least one exemplary embodiment has been presented in theforegoing detailed description of the invention, it should beappreciated that a vast number of variations exist. It should also beappreciated that the exemplary embodiment or exemplary embodiments areonly examples, and are not intended to limit the scope, applicability,or configuration of the invention in any way. Rather, the foregoingdetailed description will provide those skilled in the art with aconvenient road map for implementing an exemplary embodiment of theinvention. It being understood that various changes may be made in thefunction and arrangement of elements described in an exemplaryembodiment without departing from the scope of the invention as setforth in the appended claims.

What is claimed is:
 1. A fuselage assembly for an aircraft, the fuselageassembly comprising: a fuselage skin; a cabin liner having an outer sidefacing the fuselage skin; and an over-frame blanket assembly disposedbetween the fuselage skin and the cabin liner, the over-frame blanketassembly comprising a first blanket piece, the first blanket piececomprising: a first sound barrier layer that defines a first outersurface of the over-frame blanket assembly, and a first sound absorbinglayer that defines a second outer surface of the over-frame blanketassembly facing the fuselage skin.
 2. The fuselage assembly of claim 1,wherein the over-frame blanket assembly further includes an acousticbarrier patch and a second blanket piece, the second blanket piececomprising a second sound barrier layer that further defines the firstouter surface of the over-frame blanket assembly, wherein the acousticbarrier patch includes a sound barrier material adhered directly to thefirst sound barrier layer and directly to the second sound barrierlayer.
 3. The fuselage assembly of claim 2, wherein the acoustic barrierpatch is adhered to the first sound barrier layer and the second soundbarrier layer by an adhesive layer.
 4. The fuselage assembly of claim 1,wherein the first sound barrier layer and the first sound absorbinglayer define an entire depth of the over-frame blanket assembly.
 5. Thefuselage assembly of claim 1, further comprising a fuselage structuralmember and a retaining assembly that includes a retaining spike and aretaining cap, wherein the retaining spike is coupled with the fuselagestructural member and the retaining spike passes through an aperture inthe first blanket piece, and wherein the retaining cap is secured to theretaining spike and includes a vibration isolating layer that abuts thefirst sound barrier layer.
 6. The fuselage assembly of claim 1, furthercomprising an acoustic barrier patch and a structural component of thefuselage assembly, wherein the acoustic barrier patch includes a soundbarrier that is adhered directly to the first sound barrier layer and isadhered directly to an outer portion of the structural component.
 7. Thefuselage assembly of claim 1, wherein the cabin liner includes a soundabsorbing layer on the outer side of the cabin liner.
 8. An over-frameblanket assembly for a fuselage assembly of an aircraft, the over-frameblanket assembly comprising: a first sound barrier layer that defines afirst outer surface of the over-frame blanket assembly; and a firstsound absorbing layer that defines a second outer surface of theover-frame blanket assembly for facing a fuselage skin when installed inthe fuselage assembly.
 9. The over-frame blanket assembly of claim 8,further comprising a first blanket piece and a second blanket piece, thefirst blanket piece consisting of the first sound barrier layer and thefirst sound absorbing layer, the second blanket piece consisting of asecond sound barrier layer and a second sound absorbing layer, whereinthe second sound barrier layer further defines the first outer surfaceof the over-frame blanket assembly.
 10. The over-frame blanket assemblyof claim 9, further comprising an acoustic barrier patch that includes asound barrier material adhered directly to the first sound barrier layerand directly to the second sound barrier layer.
 11. The over-frameblanket assembly of claim 10, wherein the acoustic barrier patch isadhered to the first sound barrier layer and the second sound barrierlayer by an adhesive layer.
 12. The over-frame blanket assembly of claim1, wherein the first sound barrier layer and the first sound absorbinglayer define an entire depth of the over-frame blanket assembly.
 13. Theover-frame blanket assembly of claim 1, wherein the first sound barrierlayer is a flexible mass barrier.
 14. The over-frame blanket assembly ofclaim 1, wherein the first sound absorbing layer is formed from a flameresistant felt material.
 15. A method of installing an over-frameblanket assembly into a fuselage assembly of an aircraft, the methodcomprising: providing a first blanket piece of the over-frame blanketassembly; positioning the first blanket piece in an orientation suchthat a first sound barrier layer is directly adjacent to a cabin liner;and securing the first blanket piece to the fuselage assembly in theorientation.
 16. The method of claim 15, further comprising providing asecond blanket piece of the over-frame blanket assembly and joining thesecond blanket piece to the first blanket piece by adhering a soundbarrier of an acoustic barrier patch directly to the first sound barrierlayer and directly to a second sound barrier layer of the second blanketpiece.
 17. The method of claim 15, further comprising adhering a soundbarrier of a second acoustic barrier patch directly to the first soundbarrier layer and directly to an outer portion of a structural componentof the fuselage assembly.
 18. The method of claim 15, further comprisingcoupling a moisture control element to the over-frame blanket assembly.19. The method of claim 15, further comprising: pressing the firstblanket piece onto a retaining spike that is mounted to a frame of thefuselage assembly; and pressing a retaining cap onto the retaining spikeso that a vibration isolating layer of the retaining cap abuts the firstsound barrier layer.
 20. The method of claim 15, further comprisingsecuring a cabin liner so that an acoustic absorbing layer of the cabinliner opposes the first sound barrier layer.